Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils

Research output: Contribution to conferencePaper

22 Citations (Scopus)

Abstract

The aerodynamics of deployable devices based on Gurney flaps, miniature trailing-edge effectors, or MiTEs, is explored for rotorcraft applications using computational fluid dynamics (CFD). A Gurney flap is a small aerodynamic device, with a height of only a few percent of the airfoil chord, mounted normal to the airfoil surface near the trailing edge. A MiTE extends the Gurney flap concept by making it deployable. To support future design efforts, and because fully dynamic wind-tunnel experiments would be difficult and costly, the unsteady behavior of MiTEs is studied for a static airfoil and during airfoil-pitch oscillations using the Navier-Stokes numerical solver OVERFLOW2. Static wind-tunnel tests from low-speed wind-tunnel experiments that explore the effects of Gurney flaps at a chord Reynolds number of 1.0×10 6 are used for the calibration and verification of the CFD. The results indicate similar effects along with qualitatively correct behavior, and the trends in the predicted dynamic performance are reasonable in that they agree with unsteady circulatory theory. In addition, wind-tunnel experiments of an oscillating rotorcraft airfoil using Gurney flaps through dynamic stall are also used for validation. These experiments verify the CFD models, allowing the extension of the studies to examine the potential of MiTE for rotorcraft. Much insight is gained on the unsteady aerodynamic behavior through transonic flow conditions, at high angles of attack, and with variations in the chord-wise placement of MiTEs. Additionally, CFD is used to show that MiTEs have the ability to be used as an active stall control device. These studies show that there does not appear to be any significant shortcoming of MiTEs potential for rotorcraft.

Original languageEnglish (US)
Pages9847-9861
Number of pages15
StatePublished - Dec 1 2005
Event43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 10 2005Jan 13 2005

Other

Other43rd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/10/051/13/05

Fingerprint

Airfoils
Wind tunnels
Computational fluid dynamics
Aerodynamics
Experiments
Transonic flow
Angle of attack
Dynamic models
Reynolds number
Calibration

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Kinzel, M. P., Maughmer, M. D., Lesieutre, G. A., & Duque, E. P. N. (2005). Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils. 9847-9861. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.
Kinzel, Michael P. ; Maughmer, Mark David ; Lesieutre, George A. ; Duque, Earl P.N. / Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.15 p.
@conference{b7cfbaa8ff2340f69cb7f183b1387426,
title = "Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils",
abstract = "The aerodynamics of deployable devices based on Gurney flaps, miniature trailing-edge effectors, or MiTEs, is explored for rotorcraft applications using computational fluid dynamics (CFD). A Gurney flap is a small aerodynamic device, with a height of only a few percent of the airfoil chord, mounted normal to the airfoil surface near the trailing edge. A MiTE extends the Gurney flap concept by making it deployable. To support future design efforts, and because fully dynamic wind-tunnel experiments would be difficult and costly, the unsteady behavior of MiTEs is studied for a static airfoil and during airfoil-pitch oscillations using the Navier-Stokes numerical solver OVERFLOW2. Static wind-tunnel tests from low-speed wind-tunnel experiments that explore the effects of Gurney flaps at a chord Reynolds number of 1.0×10 6 are used for the calibration and verification of the CFD. The results indicate similar effects along with qualitatively correct behavior, and the trends in the predicted dynamic performance are reasonable in that they agree with unsteady circulatory theory. In addition, wind-tunnel experiments of an oscillating rotorcraft airfoil using Gurney flaps through dynamic stall are also used for validation. These experiments verify the CFD models, allowing the extension of the studies to examine the potential of MiTE for rotorcraft. Much insight is gained on the unsteady aerodynamic behavior through transonic flow conditions, at high angles of attack, and with variations in the chord-wise placement of MiTEs. Additionally, CFD is used to show that MiTEs have the ability to be used as an active stall control device. These studies show that there does not appear to be any significant shortcoming of MiTEs potential for rotorcraft.",
author = "Kinzel, {Michael P.} and Maughmer, {Mark David} and Lesieutre, {George A.} and Duque, {Earl P.N.}",
year = "2005",
month = "12",
day = "1",
language = "English (US)",
pages = "9847--9861",
note = "43rd AIAA Aerospace Sciences Meeting and Exhibit ; Conference date: 10-01-2005 Through 13-01-2005",

}

Kinzel, MP, Maughmer, MD, Lesieutre, GA & Duque, EPN 2005, 'Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils', Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States, 1/10/05 - 1/13/05 pp. 9847-9861.

Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils. / Kinzel, Michael P.; Maughmer, Mark David; Lesieutre, George A.; Duque, Earl P.N.

2005. 9847-9861 Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils

AU - Kinzel, Michael P.

AU - Maughmer, Mark David

AU - Lesieutre, George A.

AU - Duque, Earl P.N.

PY - 2005/12/1

Y1 - 2005/12/1

N2 - The aerodynamics of deployable devices based on Gurney flaps, miniature trailing-edge effectors, or MiTEs, is explored for rotorcraft applications using computational fluid dynamics (CFD). A Gurney flap is a small aerodynamic device, with a height of only a few percent of the airfoil chord, mounted normal to the airfoil surface near the trailing edge. A MiTE extends the Gurney flap concept by making it deployable. To support future design efforts, and because fully dynamic wind-tunnel experiments would be difficult and costly, the unsteady behavior of MiTEs is studied for a static airfoil and during airfoil-pitch oscillations using the Navier-Stokes numerical solver OVERFLOW2. Static wind-tunnel tests from low-speed wind-tunnel experiments that explore the effects of Gurney flaps at a chord Reynolds number of 1.0×10 6 are used for the calibration and verification of the CFD. The results indicate similar effects along with qualitatively correct behavior, and the trends in the predicted dynamic performance are reasonable in that they agree with unsteady circulatory theory. In addition, wind-tunnel experiments of an oscillating rotorcraft airfoil using Gurney flaps through dynamic stall are also used for validation. These experiments verify the CFD models, allowing the extension of the studies to examine the potential of MiTE for rotorcraft. Much insight is gained on the unsteady aerodynamic behavior through transonic flow conditions, at high angles of attack, and with variations in the chord-wise placement of MiTEs. Additionally, CFD is used to show that MiTEs have the ability to be used as an active stall control device. These studies show that there does not appear to be any significant shortcoming of MiTEs potential for rotorcraft.

AB - The aerodynamics of deployable devices based on Gurney flaps, miniature trailing-edge effectors, or MiTEs, is explored for rotorcraft applications using computational fluid dynamics (CFD). A Gurney flap is a small aerodynamic device, with a height of only a few percent of the airfoil chord, mounted normal to the airfoil surface near the trailing edge. A MiTE extends the Gurney flap concept by making it deployable. To support future design efforts, and because fully dynamic wind-tunnel experiments would be difficult and costly, the unsteady behavior of MiTEs is studied for a static airfoil and during airfoil-pitch oscillations using the Navier-Stokes numerical solver OVERFLOW2. Static wind-tunnel tests from low-speed wind-tunnel experiments that explore the effects of Gurney flaps at a chord Reynolds number of 1.0×10 6 are used for the calibration and verification of the CFD. The results indicate similar effects along with qualitatively correct behavior, and the trends in the predicted dynamic performance are reasonable in that they agree with unsteady circulatory theory. In addition, wind-tunnel experiments of an oscillating rotorcraft airfoil using Gurney flaps through dynamic stall are also used for validation. These experiments verify the CFD models, allowing the extension of the studies to examine the potential of MiTE for rotorcraft. Much insight is gained on the unsteady aerodynamic behavior through transonic flow conditions, at high angles of attack, and with variations in the chord-wise placement of MiTEs. Additionally, CFD is used to show that MiTEs have the ability to be used as an active stall control device. These studies show that there does not appear to be any significant shortcoming of MiTEs potential for rotorcraft.

UR - http://www.scopus.com/inward/record.url?scp=30744453544&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=30744453544&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:30744453544

SP - 9847

EP - 9861

ER -

Kinzel MP, Maughmer MD, Lesieutre GA, Duque EPN. Numerical investigation of miniature trailing-edge effectors on static and oscillating airfoils. 2005. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.